Automatic radio direction indicator system



May l2, 1942., E, J, HEFELE AUTOMATIC RADIO DIRECTION INDICATOR SYSTEM Filed April 27, 1937 4 Sheets-Sheet l IENTOR.

a-r'd; Jlefele ATTORNE May l2, 1942. E. J. HEFELE AUTOMATIC RADIO DIRECTION INDICATOR SYSTEM Filed April 27, 1937 4 Sheets-Sheet 2 R- F' 40AMPLIFIER INVENTOR. durar-d .flCefele ATTORNEY.

May 12,1942. E. J. HEFELE AUTOMATIC RDIO DIRECTION INDICATOR SYSTEM 4 sheets-shea s Filed April 27, 1937 0 R vm m5 0N i VIE. .m mL O o@ y I n 7 J l l M ANTENNA NON' ANTENNA AMPLIFIER IV ENT OR. ndward 3. JfeFele BY ATTORNEY May 12, 1942. E. J. HEI-ELE 2,282,402

AUTOMATIC RADIO DIRECTION INDICATOR SYSTEM l v Filed April 27, 1931 4 Sheets-sheet 4 l, Hz

l 7 T A T66 n R- F. rg AMPLIFIER f Y MARKER BEACON RECEIVER -o l 0J /L- Tigris INVENTOR.

ATTORNEY.

adwardafefele Patented May 12, 1942 AUTOMATIC RADIO DIRECTION INDICATOR SYSTEM EdwardJ. Hefele, Amityville, N. Y. 'y

Application April 27, 1937, Serial No. 139,142

(Cl. Z50- 11) Claims.

My invention relates to radio direction nders, and more particularly, to that type of direction nder that automatically indicates the deviation in bearing to the right or left of the desired direction. This application is a continuation-inpart of my co-pending application Serial No. 43,189, filed vOctober 2, 1935.

The determining factor in the directional characteristics of the usual direction finder using only a loop -antenna is the orientation or angular position of the loop antenna with respect to the direction of the received signal. The null point is detected by a sharp demarcation between a decreasing and increasing signal reception accordingto the angular position of the loop. Accurately controlled frequency, amplication or other electrical conditions in the associated apparatus are unnecessary since they do not aiiect the accuracy of the indicated direction. Thus, the directional accuracyof solely loop antenna reception depends upon the geometry of the loop, i. e., the angular position of the loop and is unaected by variations of the electrical constants.

In numerous situations, such as in aeroplanes, however, direction finders are insuilicient due to the experimental work necessary in rotating the loop back and forth to find the null or maximum indications. For these cases, it has been proposed to use a right-left indicator, which isa system in which bearings are automatically ascertained.

In right-left indicators heretofore proposed, however, the readings depended upon constancy of the electrical conditions of the circuits, a factor which is impractical to obtain, and accordingly no commercially ,practicalv right-left indicator system has heretofore been developed.

An early attempt at imparting a right and left sense to the direction finder was to utilize two loop antennae placed at an angle to each other (usually 90), two individually connected radio receivers, and a differentially connected indicating meter at the outputs. The normal gure-of-eight polar pattern deiined `the reception of each loop and associated amplier independently, When the loops were in on-course position, equal signals are received by them and therefore equal outputs would be fed to the differentially connected output meter. This meter was connected so that the equal outputsproduced equal and opposite deflecting torques upon the indicatingr needle, which resulted in a zero center or on'course reading. If the line of bearing was to either the right or left of the true radio bearing, one of the loop signals predominated and the receivers thus had unequal inputs applied to them from the loop antennae. There resulted unequal outputs to the indicating meter, producing a resulting indication which was either to the right or to the left of the zero center.

there are many electrical constants which re.

quirecontinual corrections and balancing. Thus the over-all amplification or gain of the two radio receivers must be equal and so maintained. In practice, this can be accomplished l for short intervals of time, and to maintain this equal gain requires repeated adjustments of the equipment. The design of the equipment must be such that the two loop antennae have equal l effective electrical heights, equal inductance and tune to exactly thesame signal frequency, necessitating a degree of precision in manufacture, and maintenance which makes such. a direction finder a very expensive precision instrument and commercially impractical. A slight misadjustment in either loop circuit results in errors where null indications occur when the station is offcourse by as much as six or seven degrees. Tests have shown that such equipment is entirely unreliable under normal operating conditions on the ground, on shipboard or in an aircraft.

The next development in the art was to remove a major disadvantage -by utilizing only one radio receiver. The components of such a system also consisted of two loop antennae placed at an angle with respect to each other, a single radio receiver, a diierentially connected indicating meter, and a switching device which alternately connected either loop to the radio receiver and at the same time switched the corresponding terminals of the indicating meter to the output of the radio receiver. The necessity of maintaining the sensitivity and tuning of two radio receivers equal was thus entirely removed. Various switching schemes were tried but it was found that mechanical switching introduced transient voltages at the radio receiver which resulted in erratic operation. Electronic switching was then developed to avoid the objectionable transients. However, bearing inaccuracies resulting from slight misadjustments in .either loop antenna circuit, together with the disadcardioid polar pattern of reception with the null' direction pointing -alternately towards the right and left of the direction of flight. The switching mechanism is arranged to alternatelyapply such right` and left hand cardioid reception pattern's to the radio receiver. An fon-course bearing produces equal signal inputs to the receiver, so that there is a resultant zero torque on the needle of the differentially connected indicating meter. The double cardioid system prior right and left indicators, Where two loops, or a loop and a vertical antenna are-used, the operation depends upona comparison of the relative signal pick-up of one loop antenna and the pick-up of either another loop or vertical antenna. A comparison of signal strengths, either arithmetically or by ratio, dependsupon'the absolute values of the resultant signal intensities. These intensities in turn are dependent upon electrical circuit conditions such as vsignal pick-up I of the loop, the tuning of the loop-circuit,`the

-; gain of the amplifier, etc. Since these elecis a great improvement over previous types of right and left indicating direction finders. A much greater percentage of the effective height of the loop antenna is utilized, resulting in a higher signal to static noise-ratio which permits bearings to be taken when the null type direction finder would not be usable. The 180 bearing ambiguity is eliminated since when the aircraft is receding from instead of approaching ,the radio transmitter, the right-left sense indication becomes reversed. Only one loop antenna is employed, reducing thev loop system aero-dynamic resistance by approximately fifty per cent. Several serious disadvantages nevertheless make this direction finder i extremely unreliable. Where it is the sole navigational instrument, as is often the case when an aircraft is flying through fog, this unreliability is dangerous because of the fact that the indicating meter will continue to indicate right and left even though the bearing may be in serious error, with no way for the operator to test for or `realize the error. l

In the practical application of this double cardioid system, adjustments must be made very often even with the most carefully designed equipment. A tuned loop circuit and an aperiodic vertical antenna circuit with resistance phasing is generally used to produce the required cardioid polar reception patterns since this combination is most satisfactory from the standpoint of sensitivity with the use of the present radio receivers. Thismost advantageous antenna combination is the source of the serious errors mentioned, for the following reasons: In order to produce the required cardioids, it is necessary to have properly phased loop and vertical antenna circuits. In operation, the loop must be exactly in resonance with the signal' frequency and be exactly in tune with an extremely selective receiver. An extreme degree of frequency stability is thus required in the receiver, particularly in the antenna stage thereof, and it must therefore not be altered from the predetermined design. Temperature control of the radio receiver circuits has been tried. However, it should be noted that lthe loop is mounted in the open air, which in itself removes any advantages due to receiver temperature control. This is particularly true in aircraft where changes as great as 2 F, per minute may occur, which act to change the electrical tuning characteristics of the loop and therefore the combined cardioid input circuit. From the above it will vbe noted that in th trical conditions are continuallyfvarying in any practical application, al1 right and leftindicators of the prior art have been unreliable, particularly for aircraft use.

summarizing, vthe single loop direction nder is reasonably accurate because it depends solely l upon the geometric or angular position of the loop. The right-left indicators heretofore known,

on the other hand, are inaccurate because they .depend not only upon the angular position of a loop but also upon uncontrollable critical electrical parameters. These critical electrical variables may be adjusted accurately at a single frequency and for a given set of temperature humidity and electrical conditions, but when these critical adjustments change because of variations of theoriginal conditions, large errors in directional accuracy result. A more serious disadvantage is that the operator is not apprised that these changes in the electrical constants have occurred so that he may make adjustments, but

instead must blindly rely on their correctness.

In the double cardioid electronically switched system, if the loop is mistuned by as littleas one per cent, a three or four degree error results at the indicator, since the indication obtained depends upon a comparison of the signal pick-up of the loop with the signal pick-up of the vertical antenna.. A two per cent mistuning error, which is a very likely practical tuning variation, will produce an indicated deviation from normal to such an extent that although the `ship may be lon its proper course, there will lbe.indicated a wide off-course direction. In suchcardioid systems employing a loop, misphasing or mistuning the resultant indication will defiectto the right or left of the null in accordance with the geometric angular position of the loop with respect to the direction of the received signals. The no1? directionally received signals are employed as a time phase and sense reference voltage for direct combination and comparison at the indicator. By avoiding the combining of the directional and non-directional signals at the antenna stage where the hereinabove described electrical misphasi-ng effects occur, to produce an indication thereof, I independently amplify these signals in accordance with my present invention and' combine them at the indicator to produce a right or left indication in accordance with the loop signal conditions.

In my co-pending application hereinabove referred to, I describe the use of a cathode ray oscillograph as the indicator where the two independently amplified antenna signals are impressed. The non-directional signals produce a vertical line fluorescent image on the oscillograph screen, which vertical line is the null reference indication. Directionally received signals deflect the vertical indication to the right or left in accordance with the magnitude and sense (right or left) of the directional signals. -When the directional signals are out-of-phase with respect to the non-directional or reference signals, the line image widens to form an ellipse, which ellipse is nevertheless properly deflected to the right or left without affecting the accuracy of produce a straight line indication on the screen.

The indications automatically deflect to the right or left of the null or central indication as the direction of the received signals is to the right or left of the geometric null position of the directional antenna. The degree of deflection of the indication is proportional to the inclination of the received radio waves with respect to the directional antenna. No bearing ambiguity exists since, with my present invention, a reverse right and left indication occurs when a reciprocal or rearward signal is received, as thoroughly explained in my co-pending application.

In aircraft applications of radio directional systems, it is desirable to reduce to a minimum the electrical disturbances due to static generated during flight through rain, snow, sleet and storms. A loop antenna may be very well shielded from the effects of such static lby provision of a `metallic shield which is grounded. However, it has heretofore been impractical to shield a vertical mast trailing wire or a nondirectional antenna in such manner since these are employed at relatively high impedance input circuits and a grounded shield would destroy their pick-up. In accordance with my present invention, I provide a suitable shielded wire antenna, which shield intercepts the rain, snow or sleet, etc. static and transmits their effect to ground through a high impedance, and the enclosed antenna Wire is substantially freed from the erratic static pulses. Such a shield is placed at high radio frequency impedance with respect to ground, and the signal pick-up of the enclosed antenna Wire is substantially freed from the erratic static impulses.

A further method of minimizing static effects on the indications of radio directional systems and more specifically on automatic right-left indicators resides in substituting a loop antenna for the non-directional antenna. By employing two coaxial loops electrostatically shielded, and orienting one with its plane in the direction of flight, and the other transverse to the flight direction, accuratebearings free of static effects are obtained. K

Blind landing systems employing marker beacons make use of ultra high frequency signals transmitted substantially vertically above predetermined points of the landing field. I provide means for visually indicating when the aircraft is within the field of the marker beacon signals using the cathode ray indicator of the right-left indicating direction finder. Such a system is a composite indicator which shows when the aircraft passes throughthe marker beacon and indicates directional sense to the directional beacons. 2 d

In accordance with my present invention, I also provide electro-mechanical indicators which are rugged and require no auxiliary power supply to operate as does the cathode-ray tube. The electro-mechanical indicator is provided with a needle pointer preferably maintained at null or on-course position with the reference or nondirectionally received signals. Such indicators are useful where a minimum of controls for the v operator are preferred. Misphasing of the two impressed signals does not affect the indicator but somewhat reduces the sensitivity of indication as will be hereinafter described in more detail.

Where the directional antenna employed is a loop, .signal errors commonly known as night effect are combined with the regular signal waves to produce a distorted pattern of directional reception by the loop. Such effects are due to the reflected skywaves which combine with the ground waves in a different plane of polary ization to produce a resultant distorted reception pattern. Night-effect is predominant during the night hours for commercial wave lengths which are unaffected in the day time. For the ultrashort waves, for example above five megacycles, so-called night effect or erroneous directional patterns due to reflected sky-waves occur in the daytime as well,due to the predominance of the sky waves at the antenna. Accordingly, a loop antenna is impractical for accurate directional guidance -on ultra-short waves, that is, above five megacycles, and is similarly undependable for night flight. Although'the accuracy of the right and left indications ofmy present invention is unaffected by night effect signal components, I provide a novel directional antenna system Awhich is free from night effect, in place of a loop antenna for my system. Thev directional antenna I prefer to use in my present invention is preferably ycomposed of a plurality of doublet antennae, at which antennae the` night effect signal components balance or cancel.

Iny a further modification of my present invention, I provide an auxiliary cathode or electron ray null indicator responsive to the directionally received signals to independently indicate the null reception condition of the directional anf tenna array. Such an indicator will produce a double check on the null indications of a right and left direction finder to add to the reliability of the system.

Where signals of relatively yhigh percentage of modulation or even over-modulation are to be used for directional guidance, I prefer to u se very sharply selective signals for my preferred indicating system to minimize the undulated effects of such high modulated signals. I prefer to employ a double or successive series of intermediate frequency conversion stages for a superheterodyne receiver whereby the high image or rejection frequency ratio at the antenna stage is maintained with a high intermediate frequency and the superior selectivity of a lor intermediate frequency is also --used to produce a resultant sharply selective output corresponding to the carrier frequency of the signals. The use of piezo-electric crystal tuned filters at the intermediate stages would further increase the selective properties of the indicator.

Wherea cathode ray tube indicator is used in a right-left indicator in accordance with my invention, a relatively high voltagel ypower supply is generally required, having a voltage of the order of 600 to 800 volts for a bright indication image. Such high voltage power supplies of the prior art were-generally bulky structures having considerable weight. I have discovered a novel high voltage power supply which is more efficient and of light weight as compared to prior systems. My novel power supply employs an audio frequency oscillator, the output voltage of which is stepped up through. ay transformer and rectified to produce the resultant high voltage output for the cathode ray tube.

Accordingly, it isvan object of my present invention to provide a novel right and left radio direction indicating system.

Another object of my present invention is to provide a novel right-left direction indicating system employing an electro-mechanical indicator producing right-left indications independent of any electrical misphasing or parameterv of the system.

A further object of my invention is to provide a novel right and left radio direction indicating system employing antennae which are substantially independent of night effect and sky-Wave reflections in ultra-short wave signalling.

Still a further object of my present invention is to provide a novel antenna system which is shielded from the effects of rain andstorm static.

Another object of my present invention is to provide novel circuit arrangements for increasing the selectivity of the amplifiers particularly useful for radio direction finder systems.

Another object of my present invention is to provide4 an independent null indicator for improving the reliability of right-left direction finder systems.

Still a further object of my present inventionis to provide a novel high voltage power supply oi high efficiency and light weight.

These and further objects of my present invention will become apparent in the following description taken in connection with the drawings, in which:

Figure 1 is a schematic electrical diagram of a preferred arrangement of my present invention.

Figure 1A is a diagrammatic showing of a fluorescent image on a cathode ray tube indicator deflected to the right and ellipsoidal in form correspondingto misphased antenna input currents.

Figure 2 illustrates a modified form for a directional antenna employing stationary external parts and being free of night effect.

Figure 3 illustrates a modified arrangement for non-directional antenna `input vto my system.

Figure 4 is a perspective illustration of an aircraft embodying a preferred rotatable directional antenna which is free of night effect, and my novel shielded directional antenna.

. Figure 5 .illustrates the construction and circuit connection of my novel shielded non-directional antenna with respect to the radio system.

Figure 6 is a cross-sectional view taken along 6-6 of Figure 5 illustrating a preferred form for my novel static shielded antenna.

Figure '7 is a modification of the static shielded antenna corresponding to the cross-sectional view of Figure 6.

Figure 8 is a diagram of my novel high voltage supply. v

Figure 9 is a diagrammatic illustration of an electrostatic needle indicator to be used in place Vaaazfioa of the cathode ray tube indicator of my linvention. v

Figures 10 and 1l are further modifications of the electromechanical indicator operating on magnetic principles. y

Figure 12 is a schematic diagram of a two4 loop antenna system for the right-left indicator for minimizing static effects.

Figure 13 is a schematic diagram of acomposite indicator for direction iinding andmarker beacon service.

Figure 14 shows how the composite indicator indicates a marker beacon signal.

In Figure 1, I schematically illustrate a completev electrical circuit arrangement for a pre-l ferred right-left radio directional system employing a cathode ray tube indicator. The basic principle of this system is disclosed in my original and' co-pending application Ser. No. 43,189 referred to above. This principle depends upon the independent reception'and ampliilcation of a directionally and non-directionally received antenna signal and their simultaneous combination at the indicator to produce an accurate right and left indication. For many practical applications, I prefer to employ the opposed doublet antenna system 20 to directionally re-` Each doublet consistsof an upper and a lower vertical mast 2|, the opposed rportions of which are connected to opposite ends ceive radio signals.

of a primary 22 of a radio frequency coupling coil. The secondary23 of the coupling coil extends toward the central axis of theantenna array 20 and is combined in parallel to the balanced transmission line`24. I prefer to electrostatically 'shield the primaries 22 from the secondaries 23 of the radio frequency coupling coils byl well lknown grounded shields 25. vThe aries 23 are preferably connected to ground potential in order to electrically balance the doublets 2|. The antenna array 20 is known in the directional antenna art as an Adcock antenna system.

' The Adcock vantenna array v2.0 employing the doublets 2| has a figure-of-eight reception pattern. Thenull reception characteristics of the antenna system 20 occurs perpendicular to the plane in which the doublets 2| lie. The polarization eifects dueto the reflected sky-waves and night eiect are eliminated by this antenna array as well known in the art. In order to practicably employ the Adcock antenna array 2|) for the right-left indicator, particularly upon an air craft, I mount the directional antenna system 20 so as to be rotatable about its central portion as indicated by the dot-dash line.` p Accordingly, the directional system 20 instead of being rigidly mounted in position upon the aircraft as in prior applications of such an antenna array, is made rotatable and usable generally in a direction nder in place of a loop antenna, and not speciflcally as a homing system. A handwheel 21 is drawn in dotted at the center of rotation to indicate its control of the orientation of the antenna system 2li.K

In Figure 4 I have illustrated the antenna system 20 positioned upon an airplane 28 and arcable 32 for adjustably positioning the antennav 2|).A The illustrated position of antenna, with its Vplane positioned parallel to the axis of the aircraft wings 28 will produce null indication for signals coming from the front or rear of the plane. It is to be understood that the vertical rods 2| are insulated with respectto the sup porting tubes 33. A mechanically simpler doublet antenna array which has an adjustable null position is illustrated in Figure 2. By using four doublets arranged in a square and corresponding to two sets of double antenna arrays crossed at right angles, a goniometer comprising a rotatable coil may be used to pick-up the resultant directional gure-of-eight pattern by combining the individual doublets 34 in a well known manner. The goniometer coil (not shown) is enclosed at 35 and by rotating this coil, the null position of the reception pattern may be varied.

The output of the goniometer is connected to the transmission line 24 connection leads which connect to the input 38 ofthe directional antenna radio frequency amplifier 31.

The non-directional antenna system may be of any preferred form. In Figure 1 I have illustrated a single doublet 38 similar to those already described and coupled to the input 40 of the nondirectional radio frequency amplifier 4I by means of an antenna coupling coil 42. Figure 3 generally indicates a non-directional antenna 43 which may be used in place of the doublet array 38. For high frequency work, namely signals of the order of five megacycles, and greater, .it is preferable to use the doublet antenna array. The over-all distance between the top and bottom of such a doublet antenna is of the order of a half-wave length and very eflicient reception of such high frequency is possible with such a system. For similar reasons, the directional doublet antenna array described in connection with Figures 1 and 2 are preferable and efficient as compared to a loop antenna for such ultrashort wave frequencies.

The antenna arrays built up of the balanced doublet illustrated in Figures `1 and 2 are designed in accordance with the principles well known in the radio communications art. I have illustrated the primaries and secondaries of the coupling coils having their midpoints electrically grounded and with electrostatic shields between the primaries and secondaries. The interconnections between the plurality of doublets are made with balanced circuits and transmission lines to produce the predetermined reception pattern at the input of the radio frequency amplifier. Although I have illustrated the combination of a plurality of doublet antennae with electrically balanced circuits interconnecting them, I do not Wish.to be limited by this application to produce the rotatable directional reception patterns with the doublet antenna for a radio direction finder. Thus, by eliminating the bottom half of the doublets and retaining the top vertical masts, a similar combination of vertical masts is had to v produce the figure-of-eight reception patterns.

In this modification, it is preferable to ground the bottom ends of all the coupling coils instead of theirI mid-points.

In Figure 4, I illustrate a trailing wire 45 corresponding to the non-directional antennae 38 and 43 of Figures 1 and 3. The trailing antenna Wire 45 is generally weighted at one end by a weight 46 and is let out from the aircraft for reception during flight. Prior single Wire antenna are seriously affected by static produced by impact of the antenna with particles of rain, sleet, snow and dust when used on high speed aircraft.

It has been heretofore considered impractical to shield such an antenna from such static effects and by my present invention I provide a practical shielding therefor which greatly reduces the static and greatly increases the signal-tostatic ratio of signals introduced by the shielded antenna wire to the radio receiver.

In Figure 5, I illustrate a preferred form of statically shielded wire antenna 45 and the electrical connections therefor. This antenna comprises a central antenna wire 41 connected to the primary of the antenna coupling coil 48 which is connected to the input 40 of the radio frequency amplifier 4|. Two metallic layers 58 and 5l are arranged concentrically about the conductor 41 and preferably` spaced and supported by alternatelayers of insulation material 52 and 53. The anti-static trailing wire modification herein disclosed in connection with Figures 5, 6, and 7 is a ground through the high impedance choke coil 54. The interior shields are also connected to ground through the high impedance choke to minimize transient impulse excitation of the antenna input circuit.

Figures 6 and 7 are preferred arrangements for the concentric shielding forthe antenna wire 41. Figure 6 consists of two concentric shields 58 and 5I having a portion of the circumference 55 slotted along its length to reduce signal losses due to- Figure 7, three concentric shields 56, 51 and 58 are arranged about the antenna conductor 41 having differently disposed slotted openings and velectrically connected to ground through a radio frequency choke coil. The high impedance connection of the shields to ground permits the radio frequency signal to be efficiently picked up by the internal antenna conductor 41 and yet permits the dissipation and conduction to ground of the static generated by the high velocity atmospheric particles.

Referring again to Figure 1, the input 36 of radio frequency amplier 31 is connected to the directional antenna 20. I prefer to employ a balanced transmission line 24 to couple the rotatable doublet antenna system 20 to the radio frequency amplifier 31. In order to maintain proper terminal impedance connections I employ a coupling transformer 58 at the end of the transmission line 24. The secondary of the coupling coil 58 is directly connected to the input 36 of the radio frequency amplifier 31. A tuning condenser 60 is shown connected in parallel across 'the secondary of transformer 58 for varably tuning the directional antenna system to the desired signals. A Vernier condenser 6I is preferably connected in parallel across the main tuning lcondenser 60 to permit manual correction of the relative phase between the output signals impressed upon an indicator. 'I'he non-directionally received signals from antenna 38 are impressed upon the input 40 of the radio frequency amplifier 4I. The doublet antenna system 38 is coupled to the transmission line 24 through an lelectrically balanced coupling transformer 42.

for the two receivers.

The end of the transmission line 24' is properly terminated by a transformer 59, the secondary of which is connected to the input 40 of the nondirectional radio frequency amplifier 4I. A tuning condenser 62 is connected in parallel across the secondary of the transformer 59 which tunes the non-directional antenna to the same received signals. A common tuning control for the whole receiver system employing a single mechanfrequency converters 63 and 64 having a common beat frequency oscillator 65. VThe output of the frequency convertors 63 and 64 are respectively introduced to the intermediate frequency amplifiers 66 and 61 which further amplify the reduced frequency signals. I prefer to employ the conventional high image ratio rejection frequency for this first intermediate frequency conversion, namely a frequency of for example 465 kilocycles as the intermediate frequency at 66 and 61. The outputs of the intermediatefrequency amplifiers 66 and 61 are respectively connected to the second frequency converters 68 and 69 having a further' common beat frequency oscillator 10. The outputs of the frequency convertors 66 and 69 are respectively connected to intermediate frequency amplifiers 1I and 12. The frequency of the signals at amplifiers 1 I and 12 are preferably of the order of 60 kilocycles, for example, 66 kilocycles. By employing such low intermediate frequency, much greater selectivity results to improve the indications at the cathode ray indicator 13 even for over-modulated conditions of the received signals.

tube may be used but intercoupling between the vertical and horizontal deecting plates should be minimized as described in my copending application already referred to.

The electron beamv 82 is focused upon the screen 83 of the cathode ray tube 13 to the central point 94 when no signals are impressed on the deilecting plates. When the non-directional signals from antenna 36 are amplified and impressed upon the vertical deflecting plates 18-19, a vertical line image 85 is produced on the screen 93 as shown in dotted in Figure 1A and corresponding to the 0 or null position of the indicator. The amplitude of the null indication65 is adjustable by the degree of amplification of the non-directional amplifier train. The directionally received signals produce a signal componet across the horizontal deiiecting plates 16 and 11 of the identical frequency asthe reference signal impressed across the plate 18--19. The combined effects of the horizontal and vertical signal components produce a resultant image upon the fluorescent screen 83 defiected to the right or left of the null position 85, the angle of the deiiection being proportional to the amplitude of the non-directionally received signals. The defiectional sensitivity of the indication to the rightl or left of (the null position depends upon the ratio of amplification between the directional 'Ihe double frequency conversion should preferably be designed so that any harmonics of the beat frequency oscillator 10 or the resultant intermediate frequencies `at 1| and 12 should not coincide with the intermediate frequency at ampliiier 66 or 61 or the frequency of the oscillator 65. Thus,'any tendency toward parasitic oscillation or regeneration between any of the stages is avoided and a very high gain system may be readily designed. Where a cathode ray indicator 13 is employed, it is preferable to use high voltage signals to obtain correspondingly larger indications on the screen of the tube.

The outputs of the second intermediate frequency amplifiers 1l and 12 are respectively cony nected to step-up transformers 14 and 15. The

secondary of the step-up transformer 14 at the end of the amplifier train for the directionally received signals is connected to the horizontal deflecting plates 16 and 11 of the cathode ray tube 13. The secondary of the step-up transformer 15, at the end of the non-directional signal amplifier train, is connected across the vertical defiecting plates 18 and 19. The midpoints of the secondaries of the transformers 14 and 16 are preferably `connected to the focusing anode 80 which is connected to the highk voltage direct current source 8|. Any conventional cathode ray and non-directional amplifier trains and may be suitably adjusted by the pilot in accordance with his immediate requirements.

The following vmathematical analysis of my invention is presented to demonstrate the freedom of the indications from any electrical variations `and misphasing. For simplicity, I shall neglect the modulation of the radio frequency carrier of the received radio signals, since the modulation of the carrier wave does not affect the indications because both the horizontal and vertical components of the applied oscillograph deflection voltages originate from the same signal and have substantially identical wave forms. I do not detect any audio frequency modulation for `the operation of the right and left indications. However, detection of the audio frequency modulation is feasible without affecting the right and left indications. An audio frequency reception unit 86 may be connected to the output of the non-directional amplifier train through the doublepole, doublethr0w switch 96 at the intermediate frequency amplifier 12 to provide continuous aural reception from the transmitterto which the directional system is tuned. A separate aural reception receiver is therefore unnecessary which is a decided advantage in aircraft.

The voltage as amplified by the non-directional amplifier-'train and as applied to the vertical Vdefiecting plates 18-19 may accordingly'be represented as en Ev sin 21rft; where Ev is the maxi- -mum value assumed by the voltage ev, and sin 21rft represents the sinusoidal nature of the signal of carrier frequency f impressed upon the non-directional antenna Il. The signal picked up by the directional antenna 20 is amplified to l a voltage en and applied to the horizontal deiiecting plates' 16-11 of the oscillograph 13; where eh= Eh.r sin (2ft-|A), El. is the maximum value that the sinusoidal voltage eh assumes, and A representsthe electrical time phase diiference between the similar voltages eh and ev as applied to the plates of the cathode-ray tube.

The time phase difference A depends on the degree of mistuning of the loop. AIt is Well known in the electronic art that if two similar voltages are applied to the two pairs of plates of a cathode-ray oscillograph, the resultant image is a straight line if these voltages are in phase of 180 out of phase. If a phase displacement exists between these voltages, the image becomes an ellipse. It is preferable to have an indication which is a, straight line. I therefore provide a tuning adjustment to change the relative phase displacement of the directional antenna 20 voltage as applied to its amplier 31 at input 36. The tuning Vernier in my preferred embodiment is a variable condenser 6| connected across the tuning condenser 60. The operator manually adjusts the Vernier 6| to cause the cathode-ray image to become a straight line.

Figure lA shows a resultant uorescent image 81 deflected at an angle 0R to the right. The indication 81 is an ellipse being the result of a misphased condition between the two corresponding voltages and angle A of the equation. Although an accurate olii-course indication is provided by the inclination of the axis 88 of the ellipse 8l, it is particularly advantageous to maintain a straight line indication on the screen 83. Accordingly, the operator manually adjusts the Vernier tuning capacity 6| or makes an equivalent adjustment until the value of angle A becomes resulting in a straight line indication corresponding to the dotted axial line 88 on the indicator screen 83. When the indication is a straight line, the time phase difference A between the two component voltages is 0 and the directional signal output eh may .be represented as En sin 21rft.

The value of the angle 0 which the indication on the uorescent screen 83 assumes, depends on the relative magnitudes of the effective values Eh and Eb. The angle 0 is equal to arctan eh/ev=arctan Erl/Ev, and the resultant magnitude of the line of deflection is proportional to since these in-phase deecting components are in quadrature. The quadrant of the deflection in this case towards R, is arbitrary and is preferably designed to correspond to a bearing to the right of the desired course when the directional antenna is maintained in the on-course position.

A straight line imag-e will be produced only when the voltages en and ev are in phase or 180 out-of-phase. However, when the apparatus is once designed for the fluorescent image 26 to deflect towards the R quadrant when en and ev are, for example, in-phase, this image will deflect towards the left or L quadrant, when the voltages eh and ev become 180 out-of-phase. Such a phase reversal occurs when the directional antenna passes through its null or cn-course position. Furthermore, if the directional antenna is oriented in other than null, or the oncourse of flight, the direction of the signal will be as indicated by the bearing or mechanical angular position of the directional antenna. The cathode ray indication will be a vertical line 85 for this directional antenna position, When the apparent direction is to the right, the image deviates towards the right or R, and similarly to L for a left indication.

Assuming that the pilot is ying radially towards a beacon or broadcasting station from which he is receiving a signal, then the directional antenna, with its null direction in the direction ofthe state will pick-up no energy. On the other hand, the vertical antenna voltage ev will be continuously impressed upon the cathoderay tube indicator, and will produce a vertical line image on the screen corresponding to dotted line 85. If the pilot now is thrown from his course, so that the transmitting station is to the left of him, then the directional antenna will pick up energy, the magnitude of which is a function of the angle which the directional antenna makes with the direction of the incoming signal. The resultant between the magnitude of the nondirectional antenna voltage ev and the magnitude of the directional antenna voltage e1 produces an image 81 or 88 as in Figure 1A, deflected to the R.quadrant. The pilot then knows that he is flying in a direction which is to the right of the transmitter. If the pilot further deflects to the right from his course, the magnitude of the signal picked-up by the directional antenna will increase, correspondingly increasing the horizontal component voltage eh. on the cathode-ray indicator 13 and the resultant image deflection is then more to the right.

The pilot is thus automatically apprised that he is moving further oif-course and towards the right of the transmitting station. `On the other hand, if he rotates his aircraft so that it approaches the line of-direction of the received signal, the signal impressed upon the directional antenna decreases in magnitude and the resultant fluorescent image approaches the vertical position 0. The pilot is then .apprised of the fact that he is approaching the line of direction to the radio station and is again on-course when the indication is a vertical line. A similar consideration is involved when he is flying ofi course towards the left of the transmitting station, except that the directional antenna produces a signal 180 out of phase with that corresponding to that received when flying towards th-e right, and the image correspondingly deviates towards the left. We thus have normal or correct right and left indications when navigatingtowards a beacon. Such an indicator is extremely useful for homing, i. e., flying to a destination transmitter by keeping the indicator image at zei-o" or center.

In the case when the pilot is flying radially away or.receding from the transmitting station instead of approaching it, then the directional antenna will again pick up no energy and a vertical image as 85 of Figure 1A will result. If now he is thrown to the right of the signal direction, the directional antenna will pick up some energy but since the orientation of the directional antenna is reversed or 180 from that condition hereinabove described, the horizontal component voltage eh will be out of phase with respect to that received hereinbefore when thrown to the right and the image will have an inclination to the L instead of R quadrant. The pilot will therefore assume that he is heading to the left of the incoming signal and therefore will turn his aircraft towards the right in orderto turn to the on-course direction. He thus turns his ship further to the right, increasing the magnitude of the resultant signal in the directional antenna and further increasing the deflection in. the L quadrant. The pilot therefore will promptly realize that he is swerving further from instead of closer to his desired course, and is thus apprised of the fact that a reversed left and right indication is occurring, that he is iiying on a reciprocal or reversed bearing and that the signal is coming from the rear rather` than from the front of his ship.

ment 6| in the directional antenna circuit provides means for properly phasing the directional antenna voltage eh with respect to the non-directional antenna voltageev to the proper or 180 phase relation. Since mistuning cannot produce a 180 phase reversal, the only possible condition for a straight line (when A equals 0) is to bring the directional antenna voltage phase to 0 or 180 to produce the proper right-left sense as designed for, dependent only upon the orientation of the directional antenna in the field of the signal. Thus, when the cathode-ray screen pattern is a straight line, the phasing has been properly adjusted irrespective of any previous conditions o`f mistuning. The component radio frequency stages of the non-directional and di- Y even reach 90. The small Vernier tuning adjustl rectional antenna amplifier trains produce a 180 reversal in phase of the voltage as the signal passes through each stage. This condition is taken care of by properly polarizing the directional antenna 20 with respect to the amplifier outputs to give normal or correct right and left indications on the oscillograph, which when once so designed, will not change.

The practical functioning of my invention is independent of any exact frequency tuning of the amplifier trains or of the directional antenna 20 by the common tuning control. Any mistuning, hence misphasing of the component signal voltages en and ev produces an elliptic pattern on the screen 83 of the oscillograph 'I3 instead of a straight line image as hereinabove described.y The pilot is thus immediately apprised of this mistuned condition, and adjusts the vernier control 6| to make the image on the screen 83 a straight line. When the pattern is a straight line, the phasing is correct, i. e., ev and eh are in phase or 180 out of phase. Hence when a vertical straight line indication appears upon the screen 83, the indicated bearing is accurate and independent of any mistuning or misphasing in the apparatus. Any variations in the over-all amplification of the signals due to practical changes of supply voltage or of other elec- 4trical parameters of the apparatus will merely change the height ofthe Vertical line image 85,

(Figure 1A) for any given input signal strength. The on-bearing indication of the vertical li'ne image is always accurate as an indication, and its amplitude may be adjusted by a suitable receiver volume control.

By arranging the right and left doublet array, or equivalent half-doublets or single vertical masts so that one may be moved forwardly and the other rearwardly to change the angular position of the plane interconnecting the right and left masts, the null or zero reception angular position of theantenna system 20 may be made to vary from the axial position of the aircraft. Although the right and left mast may be rotated about its center axis, the forward and rearward motion ofthe masts along a line parallel to the axis of the plane would permit permanent stream-line shielding of the mast 2|, and the minimumaerodynamic resistance will" continuously remain inthe direction vof flight.

n An important feature of my present invention resides in the combination with theY right-left indicator of an independent null indication unit which is used to simultaneously check the null indications of the. right-left indicator. The combination of anull indicator unit together with the right-left` indicator permits fool-proof oncourse flight with two null indications checking each other and the result is accurate since determination to the right or left is offered by the right-left indicator. In Figure 1, I illustrate the audio frequency unit 86 connected to the output of the directional amplifier train at the intermediate frequency amplier 1| through the double-pole, double-throw switch 90. 'I'he audio frequency unit 86 contains a rectifier and audio frequency amplifier train which translates the audio frequency modulations of the received signals upon the ear phones 9|. When the directional antenna 20 is on-course, null or zero audio frequency reception is received at the ear phones 9|. The null reception at 9| is simultaneously accompanied by the vertical indication corresponding to on the cathode ray tube screen 83. Signal reception from the rightror left of the directional antenna array 20 will be heard at the ear phones 9| and will be seen as a right or left deflection on the fluorescent screen 83.

An alternative form for a null indicator unit in place of the audio frequency unit 9| is the electron-ray null indicator unit 92 shown connected to the output of the directional intermediate frequency amplifier 1| through the switch 93. The electron-ray null indicator 92 comprises a small electron beam impinging on a 'nuorescent screen and forming a shadow of width varying in accordance with the intensity of the signals impressed on the directional antenna 20. The voltage output from intermediate frequency amplifier .is rectified at the indicator unit 92 to a uni-directional current of amplitude varying in accordance with the directional signal intensity. The rectified current is used to variably bias the electron beam indicator tube to produce the indications. Complete circuit arrangements and details of such an electron beam tube null indicator system as connected to a directional antenna and amplifier is disclosed in my co-pending application Serial No. 107,209, filed October 23,v 1936. Where an electron-ray null indicator unit 92 is employed in connection with the directional amplifier system, the aural reception unit 86 maybe permanently connected across the non-directional amplifier train to provide continuous aural reception.' I

The high voltage direct current source 8| used in the operation of the cathode ray tube indicator '|3 may consist of any well known source such as batteries, dynamotors and the like. For operation of the system aboard an aircraft, such prior art power supplies are too bulky, heavy and inefiicient in producing a 700 to 1000 volt source for operating the cathode ray tube. In Figure 8 I illustrate an electrical diagram of a preferred arrangement of an electronic high Voltage direct current power source operable from an ordinary anode voltage source such as 200 volts. The dynamotor |00 supplies the normal anode voltage potential, for example, 200 Volts, at terminal |0|, the heater or iilamentary voltage such as |2 volts at terminal |02,1and a ground or negative terminal |03. An audio frequency oscillator |04 is used to generate a current of audio frequencies such as 1000 cycles. The audio frequency oscillator |04 comprises a triode |05 having a tank circuit |06 connected between its cathode and control electrode |08 to determine the generator frequency. The tank circuit |06 consists of a winding |09 on the transsegments |3| and |32 of unequal size conductively connected together and arranged to rotate former connected in parallel with a con-y denser The anode ||2 of the oscillator tube is connected to a second winding ||3 of the transformer ||0, coupled vto the first Winding |09. Lead ||4 connects the anode potential of 200 volts from terminal 0| of the dynamotor |00 to the anode ||'2 through the Winding ||3. A grid leak and condenser ||5 is shown connected in series with the grid of the oscillator.

The audio frequency current flowing through the audio frequency windings |09 and ||3 of transformer |0 are stepped-up to a much higher voltage at the secondary ||6 of the transformer. The audio frequency currents are then rectified to produce unidirectional currents of high frequency. I have illustrated a rectifier tube comprising an anode ||8 connected to one side of the secondary IIB, and an indirectly heated cathode ||9 connected to the high voltage terminal |20 of the terminal block |2|. The negative high voltage terminal |22 is at the ground potential of the'system connecting to terminal |03 of the dynamotor 00.

My novel combination of a local audio frequency oscillator and rectifier with a step-up transformer therebetween readily produces the necessary high voltage low current output required for the operation of the cathode ray tube, at voltages of the order of '700 to 1000 volts, and with an efficiency of conversion of thirty-five per cent. Prior power supplies operate at approximately five per cent efficiency or less for the small power output required to operate the cathode ray tube. A further important practical advantage of such a rectifier is that a saving in weight of approximately eighteen pounds is also obtained with such a high voltage uni-directional potential source.

The principle upon which the right-left indicator of my present invention operates and, as already described in connection with Figure 1 and also my co-pending application Serial No. 43,189 is the production of a bearing indication by a right and left indicator by impressing upon the indicator the forces generated by the amplified electrical energy from a non-directional antenna system and a directional antenna system at a physical angle with respect to each other. The two forces operating at a physical angle with respect to each other deflect the indicator to the right and left in accordance with the relative magnitude and phase of the directional antenna signals with respect to the reference non-directional signals. My invention is not limited to a cathode ray tube or other electron beam indicator. In some applications it is advisable to employ a needle indicator which is rugged and requires no auxiliary power supply as does a cathode ray tube. In Figures 9, 10 and 11 I have illustrated electro-mechanical indicators connected to my system in place of the cathode ray tube and operating on thebasic principle of my present invention.

In Figure 9 I have illustrated a needle indicator |25 operating on the electrostatic principle. The electrostatic indicator comprises four quadrants |26, |21, |28 and |29 circularly arranged about a movable or rotor portion |30 comprising two oppositely disposed electrostatic within and coact-with the quadrant plates |20 to |29. The mechanical construction of the schematically indicated meter |25 is similar to established electrostatic meters. A pointer or needle |33 is shown in dotted lines as attached to the center of rotation of the rotatable member |30. IZB-|21 are electrically connected together by connection |34 to one terminal |35 at the output of the non-directional antenna amplifier train. The rotatable or central member |30 including the segments |3| and |32 are electrically connected to the associated terminal |36 lat the output of the non-directional antenna amplifier train.

The antenna system and associated ampliers for the mechanical indicator of Figure 9 are similar to those described hereinabove and illustrated in Figure 1. The non-directional antenna amplier shown at |31 represents the radio frequency or intermediate frequency output voltage from the non-directionally received signal input. A step-up transformer |38 is connected to the output of non-directional antenna amplifier |37. The secondary of the step-up transformer |38' connects to the vertical section input terminals |35-|36 for the indicator |25. The mid-point of the secondary of transformer |38 is preferably grounded to electrically balance the output thereof. A condenser |40 is shown connected in parallel across the secondary of transformer |38 to tune it to the frequency of the signal input to the transmitter |25. Where two successive stages of frequency conversion are employed, a frequency of the order of 50,000 to 60,000 cycles may be used at the indicator |25. However, I do not wish to be limited by the order of the frequency input for the mechanical indicators, which frequency may be much lower or higher than the herein indicated frequency. The alternating current input to the mechanical indicators corresponds to the signal output of the antenna systems as will be evident.

The directional antenna amplifier shown at |4| represents the corresponding output from the directionally received signals at a, frequency identical to the output of the amplier shown at |31. A step-up transformer |42 connects the output of amplifier |4| to the horizontalsection input terniinals |43|44 of the indicator |25. A con- .denser |45 is connected across the secondary of transformer grounded.

The alternating current voltage input to the vertical section at terminals |35- |36 is of substantially uniform intensity. The rotatable member |30 will be attracted to the vertical position illustrated in response to such a signal input. Although the input is alternating current, the needle will be held in a vertical position since the stationary and rotor sections simultaneously vary in potential, producing a resultant torque to hold the needle |33 in a vertical or null reference position opposite 0. The variable or directional voltage at terminals |43|44 connecting to the horizontal stationary plates |28-|29 produces ahorizontal torque component upon the movable plates lill-|32. The vertical torque position of the indicating needle |33 is not restrained by the use of springs so that the on-course or 0 indication isproduced entirely by the physical force generated by the output of the non-directional antenna receiver. The electrostatic `plates 28| 29 |42, the midpoint of which is 'I'he vertically arranged quadrants are arranged so that their electrostatic field isl sultant electrical field will be produced so that the plates |26 and |29 will have an instantaneous positive charge and plates |3| and |28 an instantaneous negative charge producing a resultant deflection to the right R. When the directional antenna is placed on the other side of null, electrostatic plates |26 and |28 will have an instantaneous positive charge and plates |3| and |29 will have an instantaneous negative charge by reason of thereversed instantaneous polarity of the second loop position with respect to the reference instantaneous polarity on the vertical plates, producing a resultant indication to the left L.

Such right and left operation will hold true for any relative time phase displacement between the outputs of the non-directional antenna and directional antenna receiver |31 and |4| respectively until such phase displacement is 90 resulting in a possibility of reversed sense but never the possibility of erroneous null indications. However, by proper receiver design, reversal of the sense indication can be readily avoided. .It is emphasized that the on-course or null indications results when the directionally received signals are a minimum or zero so that the pilot can be reliably guided toward a transmitter. Any time phase difference between the directional and non-directional signals impressed at the indicator |25 merely results in a decreased defiectional sensitivity of the meter, the decreased'sensitivity being proportional to the divergence of the phase or increased time phase difference.

I also employ a needle indicator operating o the electro-dynamometer principle to produce the right and left indicationsA similar to the system disclosed in connection with Figure 9. The input terminals |35|36 to the vertical torque component section and the input terminals |43- |44 to the horizontal torque component section correspond to the identically numeralled terminals of Figure 9. The electro-dynamometer indicator |46 comprises two stationary coils |41 and |48 preferably arranged at 90 with respect to each other and a rotatable coil |50 arranged to rotate within the stationary coils |41 and |48. A needle |5| is aflixed to the movable coil |50. The non-directional signal input is .connected to the vertical coil |41'and the rotatable coil |50 which coils are connected in parallel. When the directional signals are 0, the rotatable coil |50 will be aligned vertically by torque resulting from the physical force produced by the magnetic actions of the coils |41 and |50. The directional signals impressed upon the horizontal coil |48 produces a resultant magnetic eld upon the movable coil |50 displacing it to the right or left of the zero or null position in accordance with the instantaneous phase relation between the reference signals impressed on the vertical coil |41, the magnitude of the deflection being proportional to the signal strength of the directionally received signals which in turn depend upon the angle between the direction of the received signals and the directional antenna position.

Figure 11 is a further modication of a magnetlc needle indicator similar .to the dynamometer |46 of Figure l0 but employing permanent magnet structures to increase the sensitivity of the indicator. The electromagnetic indicator |52 comprises two stationary magnetic material structures |53 and |54 arranged at right angles with respect to each other and having respective pole faces |55 and |56 arranged in a circle to cooperate with a movable magnetic structure |51 rotatable within the pole faces. The magnetic coils |58 and |59 of the vertical and rotatable magnet structure |53 and |51 respectively are connected in parallel across the non-directional signal terminals |35.|36. The directionally received signals are impressed across the solenoid |60 of the horizontal magnet structure |54. The magnetic operation of indicator |52 is similar to that described in connection with indicator |45.

In Figure 12 I have diagrammatically indicated a preferred automatic right-left indicating system for minimizing the effects of static upon the indications. In this case, I employ two loop antennae |10 and |1| respectively connected to the inputs of radio frequency amplifiers |12 and |13. Loop antennae |10 and |1| are preferably co-axial and mechanically connected together at with respect to each other as illustrated. The loop antennae |10 and |1| are rotatably mounted upon the aircraft in order to enable the pilot to take a null bearing in any direction. The antennae |10 and |1| are electrostatically shielded according to principles well known in the art so that they individually are free of or receive a. minimum of electrostatic disturbances. The antennae |10 and |1| are proportioned as disclosed in my Patent No. 2,062,129 for enclosure Within the streamlined housing |14 indicated in dotted line. The housing |14 is xedly attached to the aircraft and is mounted with a minimum aerodynamic resistance in the direction of ight.

The illustrated position of the loop antennae |10 and |1| will produce a null or vertical line indication upon the cathode ray screen |15 for stations directly in .line with the axis of the streamlined housing |14 and parallel with the plane of the loop |1| and perpendicular to the plane of the loop |10. The loop |10 corresponds to the directional antenna of the right-left indicator hereinabove described in connection with Figure 1 and also disclosed in my'co-pending application Ser. No. 43,189. Antenna |10 is tuned to the signal frequency by variable condenser |18. The signals from loop antenna |10 are amplified by radio frequency amplifier |12, the output of which is directly connected to the horizontal plates l11|19 of the 4cathode ray tube indicator |15 by radio frequency transformer |84. 'I'he Vernier variable condenser |19 is used for phasing control of the indication hereinabove described in connection with Figures 1 and 1a.

'I'he loop antenna |1| is tuned to the common signal frequency for the system by variable condenser |80, the signals of which are amplified by radio frequency amplifier |13 and introduced to the vertical defiecting plates IBI-|82 of the cathode ray indicator |15 by radio frequency transformer |83. The loop antenna |1| operates in place of the non-directional antenna described in'connection with Figures 1 and 3 hereinabove for the system. Although I have indicated simple radio frequency amplification for the signals, it is to be understood that frequency conversion to intermediate frequencies is feasible for the present modification.

` conditions.

A vertical line indicationon indicator |15 Ywill occur when the plane of the horizontal loop antenna |18 is perpendicular to the direction of the station so that a zero signaloutput will occur from the transformer |8| upon the horizontal deflecting plates |11|18. At this time, the vertical loop antenna.v |1| will receive a maximum signal intensity which is impressed upon the vertical deiiecting plates IBI-|92'. A vertical line indication corresponding to the dotted line 85 in Figure 1a will take place at this time to indicate an on-course indication corresponding to the position of the loops as will now be evident. For a right or left deviation with respect to the on-course position of the loops |10|1|, corresponding right-left deflections will occur upon the indicator in a manner described hereinabove, since the horizonta1" loop antenna |10 will receive signals and impress them upon the horizontal deflecting plates |11-|18 with intensity varying in accordance with the angle from the perpendicular position to loop |10. Since antennae |10 and |1| are substantially free of static pulses from which they are shielded, the signals impressed upon ampliers |12 and |13 as well as upon the cathode ray tube indi- .cator |15 will not be influenced by such static conditions which occur in thunder storms and nights through rain, sleet, snow and the like.

'Ihe cathode ray tube indicator of my present invention may be advantageously employed as a composite indicator forv both directional rightleft de terminations as well as marker beacons indicators for landing purposes. Several line landing systems have recently been commercialized employing ultra-high frequency signal communication between the landing eld and the pilot about to land. Such systems .are particularly useful for landing during fog, rain or snow Several directional ultra-high frequency transmitters are stationed along the landing field in the path of the landing direction and are arranged to transmit the ultra-high frequency signals in a vertical radiation pattern directly above the respective transmitters. Frequencies of the order of sixty megacycles are.

commonly used. The marker. beacon receiver of the pilot is tuned to the particular frequency of the marker beacon signals and when the audio frequency modulation of the signals is apparent to the pilot, he knows that he is ying through the directionally radiated marker signals and that the airplane is located directly above the predetermined marker position. A flying technique employing two or more of such marker beacons is used to effect perfect blind landing.

In Figure 13 I have illustrated in simplied schematic form the operation of the cathode ray right-left indicator used as a composite indicator in conjunction with the marker beacons. The loop antenna |85 is tuned by condenser |86 to the transmitter for directional indication. Signals describe in my co-pending application Ser. No. 43,189 and may also be any preferred modification other than straight radio frequency amplification shown here for simplicity. The system of Figure 1 of the present application for example may be used instead. The important feature of this modified form of the invention resides in the use of the marker beacon receiver |95 coupled to the antenna |96 and tuned to the predetermined marker beacon frequency for example sixty megacycles. Y The marker beacon signals are amplified and preferably demodulated so that the audio frequency modulation of the marker beacon signals are impressed upon the audio frequency transformer |91. The output of the audio frequency transformer |91 is connected to the horizontal deflecting plates IBB-|89 through radio frequency choke coils |98 and |99 connected in series with the secondary leads of transformer |91. The radio frequency choke coils |98 and |99 prevent the high frequency currents impressed upon the horizontal defiecting plates |88|89 from being short-circuited or being affected by the circuit connection of the marker beacon receiver or transformer.

The signals from marker beacon |95 when impressed upon the horizontal deflecting plates |88 and |89 cause the signals impressed upon the vertical deflecting plates I 93| 94 to literally spreadout for example as shown by the curve 200 upon the screen of the cathode ray tube |90 as shown in Figure 14. Such a spreading-out of the image upon the cathode ray screen clearly differentiates from the right and left directional indications and occurs even though the ship is voncourse and receives no signals upon the directional antenna I85. As will now be evident, the continuously impressed signals by radio frequency l amplifier |92 from the non-directional antenna horizontal deflecting plates or employ any interfrom loop |85 are passed through radio frequency amplifier |81 and are impressed upon the horizontal deiiecting plates |88 of the cathode rayl tube |90. Cathode ray tube |90 corresponds to |9| occur across the vertical deflecting plates |93-|'99. The output of the marker beacon receiver |95 is substantially zero except when its antenna |98 comes within the directionally radiated ultra-high frequency field corresponding to the marker beacon signals. At that instant, the output of the marker beacon receiver |95 will be impressed upon the horizontal deflecting plates screen corresponding to the image 200 of Figure 14. Although I prefer to use the audio frequency moduation components of the marker beacon signals, it is equally feasible to use the ultra-high frequency signals directly upon the mediate frequency corresponding to the marker beacon signals.

The composite indicator operates normally as an automatic right-left indicator in accordance with the principles hereinabove described for my invention and the marker beacon receiver causes a characteristic distortion or spreading-out of the image and produces an indication which the pilot immediately hows corresponds to the marker beacon receiver signals. The marker beacon receiver is generally disconnected during normal flight conditions and is connected in circuit before landing and the radio directional indicator |90 serves as the indicator for the marker beacon as will now be evident.

Although I have illustrated preferred embodiments for carrying out the principles of my present invention, it is to be understood that modiilcations Athereof will be evident to those skilled in the art, and accordingly I do not intend to be limited except as set forth in the following claims.

I claim:

1. In a right-left indicating direction 'finding system, a non-directional antenna; a` directional antenna; a radio frequency amplifier for each of said antennae; an electro-mechanical indicator having fixed members and unrestrained movable members; circuit connections from said radio frequency amplifiers to said fixed and to said movable members for applying radio frequency signals thereto; said movable and fixed members coacting on each other to produce arotation of said movable member to indicate the relative values of the signals in said amplifiers when energy is being received from each of said antennae, and to maintain said movable member at its zero position when energy is received from said non-directional antenna and substantially no energy is received from said directional antenna.

2. In a right-left indicating direction finding system, a non-directional antenna; a directional antenna; a radio frequency amplifier for each of said antennae; an electrostatic indicator having fixed and movable members; circuit connections from said radio frequency amplifiers to 'said xed and to said movable members for applying radio frequency signals thereto; said movable and fixed members coacting on each other to produce a rotation of s aid movable member to indicate the relative values of the signals in said amplifiers, said movable vmember being normally maintained at a zero position by energy supplied thereto from the non-directional antenna.

3. In a right-left indicating direction finding system, a non-directional antenna; a directional antenna; a radio frequency amplifier for each of said antennae; and an electrostatic indicator, said electrostatic indicator comprising a movable part and a stationary part, the stationary part being connected to one of said amplifiers and the movable part to the other of said amplifiers and being in electrostatic relation with each other.

4. In a right-left indicating direction finding system, a non-directional antenna; a directional antenna; a radio frequency amplifier for each of said antennae; and an electromechanical indicator, said electromechanical indicator comprising an unrestrained movable part and a stationary part, the stationary part being connected to one of said amplifiers and the movable part to the other of said amplifiers and being in' electromechanical relation with each other, said movable part being normally maintained at a zero position by energy supplied thereto from the nondirectional antenna.

5. In a right-left indicating direction finding system, a non-directional antenna; a directional antenna; a radio frequency amplifier for each of said antennae; an indicator having an unrestrained movable part and a stationary part, the stationary part being connected to one of said amplifiers and the movable part being connected to the other of said amplifiers, whereby said indicator is operated by the radio frequency signals of said amplifiers; to indicate the relative values of the signals in 'said amplifiers ywhen energy is being received from each of said antennae and to maintain said movable member at said elements; a non-directional antenna; means for applying signals from said non-directional antenna on the other of said elements; the resultant electrostatic field between said elements producing a relative movement therebetween for indicating the relative values of said signals from said antennae.

7. In a right-left indicating direction finding system, an electrostatic indicator comprising 'a plurality of fixed and unrestrainedinovable elements arranged circumferentially; a directional antenna, certain of said elements of said electrostatic indicator being connected thereto; and a non-directional antenna, the remaining of said elements being connected \t`o said non-directional antenna.

8. In a right-left indicating direction finding system, an electrostatic indicator comprising four quadrants circumferentially arranged; al rotor portion; a directional antenna; means for applying signals from said directional antenna to certain of said quadrants; a non-directional antenna; and means for applying signals therefrom to the remainder of said quadrants.y

9. In a right-left indicating direction finding system, an electrostatic indicator comprising four stationary quadrants circumferentially arranged; a rotor portion comprising two oppositely disposed electrostatic segments conductively connected together and arranged to rotate within and co-act with said quadrants; a directional antenna; means for connecting a pair of oppositely disposed quadrants to said directional antenna; a

non-directional antenna; and means for connecting the remaining pair of oppositely disposed quadrants to said non-directional antenna.

l0. In a right-left indicating direction finding system, an electrostatic indicator comprising four stationary quadrants circumferentially arranged;

a rotor portion comprising two oppositely disposed electrostatic segments conductively connected vtogether and arranged to rotate within and co-act with said quadrant; a directional antenna; means for connecting a pair of oppositely disposed quadrants to said directional antenna; a non-directional antenna; and means for connecting the remaining oppositely disposed quadrants and said rotating segments to said non-directional antenna. v

^ EDWARD J. HEFELE. 

